• Proceedings of the Computational Structural Engineering Institute Conference
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• 2009.04a
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• pp.492-495
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• 2009

본 논문에서는 유한대판법(Finite Strip Method, FSM)을 이용하여 복합재료로 구성된 박판구조물의 좌굴해석을 수행하였다. 유한대판법에서의 변위장은 정현곡선으로 구성된 X방향 성분과 여현곡선의 Y방향 성분으로 구성되어 있는 면내성분, 면외성분으로 횡방향으로 3차 다항식과 보 진동함수를 사용하여 구성되었다. 각 적층판의 강성을 두께방향으로 적분하여 전체 강성을 구하고 최소 포텐셜 에너지 이론을 사용하여 구한 평형방정식에 대입하여 전체 강성행렬을 구하였다. 자유도의 감소로 인한 해석시간의 단축, 입력자료 작성 및 출력이 쉬운 점들이 유한대판법을 이용한 좌굴해석의 장점이다.

• Steel and Composite Structures
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• v.42 no.4
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• pp.447-458
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• 2022

Cold-formed steel (CFS) sections are thin-walled, therefore, more susceptible to different types of geometric imperfections. Global type of geometric imperfections has a significant impact on the load-carrying capacity of flexural members. This paper reports an experimental study that discusses the influence of global imperfections on the flexural response of CFS built-up I-beams composed of two lipped channels, with simply supported ends, under four-point loading. Global imperfections of magnitude over eight times the maximum permissible ones were induced in the specimens, leading to their distress. Using various simple stiffening schemes, the capacity and stiffness of the distressed specimens were improvised. The performance comparisons were made based on the maximum loads resisted, flexural stiffnesses offered, and failure modes experienced by the specimens. As experimental data on such distressed specimens are currently lacking in the literature, the test results of the present study will provide the necessary data needed by future researchers to numerically extend this study further, which will help in the development of necessary design guidelines for the same. The stiffening schemes significantly improved the structural efficiency of distressed specimens in terms of strength and stiffness, by over 60%. As a result, an effective and time-saving solution to such realistic structural engineering problems is given.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.2
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• pp.139-146
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• 2009

In this study, an assessment is made for the helicopter vibration reduction of composite rotor blades using an active twist control concept. The piezoceramic shear actuation mechanism along with elastic couplings of composite blades is used for vibration reduction. The rotor blades are modeled as composite box-beams with actuator layers bonded on the outer surfaces of the thin-walled section. The governing equations of motion for helicopter blades are obtained using Hamilton's principle. A time domain unsteady aerodynamic theory with free wake model is used to obtain the airloads. Various rotor configurations with different elastic couplings with appropriate actuator placement are used to investigate the hub vibration characteristics. Numerical results show that a substantial reduction of $N_b$/rev hub vibration can be achieved using the optimal control algorithm.